Advanced Life Support Research and Technology Development Metric

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An Advanced Life Support System (based on physicochemical technologies and estimates for TransHab)Air Revitalization System Technology Assumed [Program] / Notes Mass [kg] Resupply [kg] Volume [m³] Power [kW] Cooling [kW]Air Pressure ARPCS [X-38] 74.0 11.1 0.41 0.100 0.100Oxygen/Nitrogen Storage high pressure [Space Transportation System (STS)] 284.0 0 1.21 0.008 0.008Humidity Control anti-microbial condensing heat exchanger [LMLSTP Ph IIA] 46.0 6.9 0.26 0.400 0.400Air Temperature Control anti-microbial condensing heat exchanger [LMLSTP Ph IIA] 99.0 14.9 0.74 0.370 0.370Carbon Dioxide Removal [Node 3] 176.0 13.8 0.45 0.365 0.365Carbon Dioxide Reduction (a) Sabatier 31.0 4.2 0.44 0.130 0.130Oxygen Production (a) Solid Polymer Water Electrolysis (SPWE) 120.9 18.0 1.12 1.840 1.840CO 2 Reduction/O 2 Production (b) Salad Machine / This item is carried in food production.Trace Contaminant Control [Node 3] 77.0 5.6 0.14 0.128 0.128Particulate and Microbe Control reusable filters 7.0 1.1 0.08 0 0Air Pressure Monitoring sensors [International Space Station (ISS)] 2.0 0.3 0 0.005 0.005Air Composition Monitoring [Space Transportation System (STS)] 6.0 0.9 0 0.015 0.015Fire Detection and Suppression smoke detector and halon 19.0 2.9 0.05 0.050 0.050Crew Cabin Volume [TransHab] / The mass of gas is assumed to be elsewhere. 300.00Water Recovery System Technology Assumed [Program] / Notes Mass [kg] Resupply [kg] Volume [m³] Power [kW] Cooling [kW]Urine Pretreatmentflush + solid agent / This item is included in water storage.Urine Processing Bioreactor + Reverse Osmosis + Air Evaporative Subsystem 175.0 87.0 0.60 1.450 1.450Hygiene Waste Storage Bladder-less tanks 203.0 0.64Hygiene Waste Processing Bioreactor + Reverse Osmosis + Air Evaporative Subsystem 76.0 6.9 0.99 0.200 0.200Hygiene Waste Post Processing Milli-Q + ammonia removal 56.0 8.0 0.55 0.540 0.540Microbial Control iodine microbial check valve 10.0 1.5 0.012 0.012Water Quality Monitoring Water Quality Monitoring (WQM) [ISS] 39.0 5.9 0.08 0.100 0.100Potable Water Storage bladder-less tanks 950.0 1.61 0.020 0.020Waste Handling & Processing Technology Assumed [Program] / Notes Mass [kg] Resupply [kg] Volume [m³] Power [kW] Cooling [kW]Urine CollectionWaste Management Subsystem [ISS] / This item is included with feces collection.Urine Storage bladder-less tanks 49.0 0.32Feces Collection and Storage Waste Management Subsystem [ISS] 103.0 15.5 1.28 0.340 0.340Other Solid Wastes trash compactor [International Space Station (ISS)] 27.0 4.1 0.09 0.060 0.060Solid Waste Processing stabilization + disposal and incineration 225.0 33.8 2.38 0.265 0.265Solid Waste Disposal overboard jettison [International Space Station (ISS)] 59.0 8.9 1.77 0.130 0.130Miscellaneous Technology Assumed [Program] / Notes Mass [kg] Resupply [kg] Volume [m³] Power [kW] Cooling [kW]Food Supplystorage [ISS] and on-board production / This item is included in Crew Accommodations; 100% food provided.Regenerative Food Production Salad Machine / Less than 10% production. 120.0 18.0 1.94 0.650 0.650System Monitoring and Control intelligent monitoring and control (M&C) 20.0 3.0System Operations Planning artificial intelligence (AI) expert system / Included in M&CCrew Accommodation System Technology Assumed [Program] / Notes Mass [kg] Resupply [kg] Volume [m³] Power [kW] Cooling [kW]Food 1.725 kg/(person•day) 8,280.0 8.28Clothes 0.267 kg/(person•day) 1,279.2 1.28Laundry 118.2Totals 12,739.4 271.8 326.70 7.178 7.178
Advanced Life Support Research and Technology Development MetricFor the Metric, the following infrastructure costs are assumed:Infrastructure Costs Transit Surface UnitsPressurized Volume 0.015 0.48 m³/kgPower 12 18 W/kgHeat Rejection 47.5 15 W/kgThe infrastructure costs here represent the incremental costs for pressurized volume,power, and heat rejection. Additionally, a crew time cost is presented based on each case.For the transit mission segment, the MTV and ERV use modules with rigid shells. Poweris provided by converting solar energy to electricity using photovoltaic cells. On thesurface, any additional volume above and beyond what is provided by the MTV isprovided by an inflatable structure. Power is provided by Brayton conversion from anuclear power plant of the SP100 class sized to generate 100 kW continuously. In bothcases, lightweight, inflatable systems are used for heat rejection. The differences in heatrejection costs reflect differences in the thermal environment on the surface of Marscompared to that of interplanetary space.Equivalent System Mass for ISS ECLSS Technology BaselineIn the tables which follow, the ISS ECLSS technology LSS have been resized for acrew of six versus the four crew in the baseline for the LSS of the USOS. Appropriateduration and infrastructure equivalencies have also been applied.ISS ECLSS BaselineCrew 4 peopleDuration 3,650 daysMass[kg]Volume[m³]Power[kW]Cooling[kW]Fixed Values 2,031 271 7.08 6.83Time DependentValuesCrew Time[per•hr/kg]ResupplyMass[kg/yr]ResupplyVolume[m³/yr]91 9,922 9.96ISS ECLSS Baseline modified for Mars Design Reference MissionCrew 6 peopleDuration 2340 daysMass[kg]Volume[m³]Power[kW]Cooling[kW]Fixed Values 3,046.5 406.5 10.6 10.2Time DependentValuesCrew Time[per•hr/kg]ResupplyMass[kg/yr]ResupplyVolume[m³/yr]136.5 14,883.0 14.9
Page 1 and 2: IntroductionAdvanced Life Support R
Page 3 and 4: Number of Crew per Mission 6Transit
Page 5 and 6: International Space Station Environ
Page 7: For clothing, a laundry is assumed.
Page 11 and 12: The ALSS technologies yield signifi

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